CN114476015B - Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle part quick detach mechanism and unmanned aerial vehicle Download PDFInfo
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- CN114476015B CN114476015B CN202210308853.6A CN202210308853A CN114476015B CN 114476015 B CN114476015 B CN 114476015B CN 202210308853 A CN202210308853 A CN 202210308853A CN 114476015 B CN114476015 B CN 114476015B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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Abstract
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle component quick-release mechanism and an unmanned aerial vehicle. The quick-release mechanism of the unmanned aerial vehicle comprises a first connecting piece, a second connecting piece, a connecting seat and a locking piece; the first connecting piece is used for connecting the first component; the second connecting piece is used for connecting a second member; the connecting base is provided with a connecting cavity for the first connecting piece and the second connecting piece to extend into; the first end of the first connecting piece extends into the connecting cavity, and the first end of the second connecting piece extends into the connecting cavity and at least partially overlaps with the first end of the first connecting piece; the locking piece penetrates through the overlapped part of the first connecting piece and the second connecting piece and locks the first connecting piece, the second connecting piece and the connecting seat. The beneficial effects of the invention are: simple structure, low cost, simple, quick and convenient disassembly and assembly operation.
Description
Technical Field
The invention relates to the field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle part quick-release mechanism and an unmanned aerial vehicle.
Background
With the development of industrial unmanned aerial vehicles, the industrial unmanned aerial vehicles are more and more widely applied to the aspects of mapping, geological surveying, disaster monitoring, meteorological detection, air traffic control, border patrol monitoring, emergency rescue, logistics, military use and the like.
Present unmanned aerial vehicle only can satisfy the flight demand, and some part structures are complicated moreover, correspond the equipment, dismantle and accomodate and inconvenient. Especially, the emergency rescue, air traffic control, border patrol monitoring and other applications cannot be assembled or disassembled quickly, so that serious consequences are easily caused.
Disclosure of Invention
In view of the above disadvantages of the prior art, an object of the present invention is to provide a quick release mechanism for components of an unmanned aerial vehicle and an unmanned aerial vehicle, which are used to solve the problem of inconvenient assembly, disassembly and storage of components of an unmanned aerial vehicle in the prior art.
To achieve the above and other related objects, the present invention provides a quick release mechanism for components of an unmanned aerial vehicle, comprising:
a first connecting member for connecting the first member;
a second connecting member for connecting a second member;
the connecting base is provided with a connecting cavity group for the first connecting piece and the second connecting piece to extend into; the first end of the first connecting piece extends into the connecting cavity group, and the first end of the second connecting piece extends into the connecting cavity group and is at least partially overlapped with the first end of the first connecting piece;
the locking piece penetrates through the overlapping parts of the first connecting piece and the second connecting piece and locks the first connecting piece, the second connecting piece and the connecting seat.
Optionally, the first connecting piece and the second connecting piece are located on two opposite sides of the connecting seat.
Optionally, the first end of the first connecting piece faces the second connecting piece, and is provided with two first lugs distributed along the longitudinal direction, and the first end of the second connecting piece is at least partially overlapped with the first lugs.
Optionally, the first end of the second connecting piece faces the first connecting piece, and is provided with two second lugs distributed longitudinally; the two second lugs are located between the two first lugs, or the two first lugs are located between the two second lugs, or the two first lugs and the two second lugs are alternately distributed along the longitudinal direction.
Optionally, the shape of the connecting cavity group is matched with the shape of the first connecting piece and the second connecting piece, so as to limit the rotation of the first connecting piece and the second connecting piece.
Optionally, connect the chamber group including at least one connection chamber, connect the chamber along horizontal setting, be equipped with the first connecting hole that is used for installing the retaining member on the connecting seat, first connecting hole is along vertically setting and passing connect the chamber.
Optionally, the connection cavity group includes two connection cavities distributed along the longitudinal direction, the first connection piece extends into one of the two connection cavities, and the second connection piece extends into the other of the two connection cavities.
Optionally, the first connecting piece and the second connecting piece are provided with second connecting holes longitudinally arranged, and the locking piece penetrates through the first connecting holes and the second connecting holes to lock the first connecting piece, the second connecting piece and the connecting seats.
Optionally, one of the first connecting piece and the second connecting piece has a structural strength greater than that of the other.
Optionally, the locking member is a bolt or a ball head locking pin with a self-locking structure.
In addition, in order to realize above-mentioned purpose, this application still provides an unmanned aerial vehicle, include as above unmanned aerial vehicle quick detach mechanism, still include interior wing subassembly and outer wing subassembly, interior wing subassembly links to each other with first connecting piece, outer wing subassembly links to each other with the second connecting piece.
Optionally, the unmanned aerial vehicle further comprises a vertical component, the inner wing component and the outer wing component are located on two opposite sides of the vertical component and are connected with the vertical component through a first connecting piece and a second connecting piece respectively.
Optionally, the connecting seat is installed in the hanging-up component, the connecting cavity group is transversely arranged, and openings corresponding to and communicated with the connecting cavity group are arranged on two opposite sides of the hanging-up component.
Optionally, the top of the vertical component is provided with a third connecting hole arranged along the longitudinal direction, and the lower end of the locking component penetrates through the third connecting hole and extends into the vertical component to lock the first connecting piece, the second connecting piece and the connecting seat.
Optionally, the retaining member is connected to the drop assembly by a flexible connection.
Optionally, the structural strength of the first connecting piece is greater than the structural strength of the second connecting piece.
Optionally, the inner wing assembly includes an inner wing skin and an inner wing connecting beam mounted within the inner wing skin and connected to the second end of the first connector.
Optionally, the outer wing assembly includes an outer wing skin and an outer wing connecting beam mounted within the outer wing skin and connected to the second end of the second connector.
Optionally, the first connecting piece, the second connecting piece, the connecting seat, the outer wing assembly, the inner wing assembly and the hanging assembly are made of aluminum alloy materials.
As mentioned above, the quick release mechanism for the components of the unmanned aerial vehicle and the unmanned aerial vehicle at least have the following beneficial effects: simple structure, low cost, simple, quick and convenient disassembly and assembly operation.
Drawings
Fig. 1 is a schematic partial structural diagram of an embodiment of an unmanned aerial vehicle according to the present invention;
figure 2 shows an exploded view of the drone of figure 1;
fig. 3 shows a top view of the drone of fig. 1;
FIG. 4 shows a cross-sectional view A-A of FIG. 3;
FIG. 5 is a schematic view of the connection of the inner wing assembly of FIG. 1 to a first attachment member;
FIG. 6 is an exploded view of the inner wing assembly and the first link shown in FIG. 1;
FIG. 7 is a schematic view of the connection of the outer wing assembly of FIG. 1 to a second attachment member;
FIG. 8 is an exploded view of the outer wing assembly of FIG. 1 and a second link;
FIG. 9 is a schematic view of the construction of the plumbing assembly of FIG. 1;
FIG. 10 is an exploded view of the drop assembly of FIG. 9
Fig. 11 is a cross-sectional view of an alternative embodiment a-a shown in fig. 3.
Description of reference numerals
1-a first connector; 11-a first lug; 12-a second connection hole; 2-a second connector; 21-a second lug; 3-a connecting seat; 31-a connecting lumen; 32-a first connection hole; 4-a locking member; 5-an inner wing assembly; 51-a first inner wing skin; 52-a second inner wing skin; 53-a first inner wing connecting beam; 54-a second inner wing connecting beam; 6-an outer wing assembly; 61-a first outer wing skin; 62-a second outer wing skin; 63-a first outer wing connecting beam; 64-a second outer wing bridge; 7-a plumbing assembly; 71-a first drop-up skin; 72-a second drop-up skin; 73-third connection hole; 74-opening.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention.
Please refer to fig. 1 to 11. It should be noted that the drawings provided in the present embodiment are only for illustrating the basic idea of the present invention, and the components related to the present invention are only shown in the drawings rather than drawn according to the number, shape and size of the components in actual implementation, and the type, quantity and proportion of the components in actual implementation may be changed freely, and the layout of the components may be more complicated. The structures, proportions, sizes, and other dimensions shown in the drawings and described in the specification are for understanding and reading the present disclosure, and are not intended to limit the scope of the present disclosure, which is defined in the claims, and are not essential to the art, and any structural modifications, changes in proportions, or adjustments in size, which do not affect the efficacy and attainment of the same are intended to fall within the scope of the present disclosure. In addition, the terms "upper", "lower", "left", "right", "middle" and "one" used in the present specification are for clarity of description, and are not intended to limit the scope of the present invention, and the relative relationship between the terms and the terms is not to be construed as a scope of the present invention.
Before describing embodiments of the present invention in detail, the present invention will be described in an application environment. The technology of the invention is mainly applied to the quick-release connecting structure, in particular to the field of unmanned aerial vehicles. The invention solves the problems of inconvenient assembly or disassembly operation, low disassembly and assembly efficiency and the like of components of the unmanned aerial vehicle.
Referring to fig. 2-8, 10 and 11, in one embodiment, the present application provides a quick release mechanism for a component of a drone, comprising a first connector 1, a second connector 2, a connecting seat 3 and a locking member 4. Wherein the first connecting piece 1 can be used for connecting a first member; the second connector 2 may be used to connect a second member; a connecting cavity group into which the first connecting piece 1 and the second connecting piece 2 extend is arranged on the connecting seat 3, the first end of the first connecting piece 1 extends into the connecting cavity group, and the first end of the second connecting piece 2 extends into the connecting cavity group and at least partially overlaps with the first end of the first connecting piece 1; the locking member 4 passes through the overlapped portion of the first and second connecting members 1 and 2 and locks between the first and second connecting members 1 and 2 and the connecting holder 3. Alternatively, the overlapping portions of the first connecting member 1 and the second connecting member 2 may be directly overlapped or indirectly overlapped, that is, the first end of the first connecting member 1 and the first end of the second connecting member 2 may be directly in contact, attached and overlapped, or overlapped but not in direct contact, attached and overlapped.
Make only need to operate retaining member 4 and just can accomplish the dismouting of first connecting piece 1, second connecting piece 2 and connecting seat 3 through the cooperation of first connecting piece 1, second connecting piece 2, connecting seat 3 and retaining member 4, reduce quick detach face and pass power route, not only reduced part quantity, simplified the structure, dismouting easy operation, quick, convenient moreover.
Referring to fig. 3, 4, 5 and 7, in an embodiment, the first and second connecting members may be components of the drone that need to be assembled together, for example the first connecting member may be, but is not limited to, the inner wing assembly 5 and the second connecting member may be, but is not limited to, the outer wing assembly 6.
Referring to fig. 3 and 4, in one embodiment, the first connector 1 and the second connector 2 are located on opposite sides of the connecting socket 3.
Referring to fig. 3 and 4, in an embodiment, the first end of the first connecting member 1 faces the second connecting member 2, two first lugs 11 distributed along the longitudinal direction are arranged on the first end of the first connecting member 1, and the first end of the second connecting member 2 at least partially overlaps the first lugs 11. Furthermore, the first end of the second connecting member 2 faces the first connecting member, two second lugs 21 distributed along the longitudinal direction are arranged on the first end of the second connecting member 2, and the second lugs 21 are at least partially overlapped with the first lugs 11. Optionally, two second lugs 21 are located between the two first lugs 11; alternatively, or both first lugs 11 are located between two second lugs 21; alternatively, the two first lugs 11 and the two second lugs 21 are alternately arranged in the longitudinal direction, that is, one of the two first lugs 11 is located between the two second lugs 21, and one of the two second lugs 21 is located between the two first lugs 11. Simple structure, butt joint convenient operation reduces the assembly degree of difficulty.
Referring to fig. 3 and 4, in an embodiment, the shape of the connection cavity set may be adapted to the shape of the first connection element 1 and the second connection element 2, so as to limit the rotation of the first connection element 1 and the second connection element 2, i.e. the outer contour of the first connection element 1 and the second connection element 2 is limited by the connection cavity set, so as to limit the rotation of the first connection element 1 and the second connection element 2 in the horizontal direction and the vertical direction. First connecting piece 1, second connecting piece 2 and connecting seat 3 mutually support, can restrict first connecting piece, second connecting piece at the one-way movement of horizontal direction and the rotation of horizontal direction, can restrict first connecting piece, second connecting piece again at the removal of vertical direction and the rotation of vertical direction, and spacing reliable and stable.
Referring to fig. 3 to 10, in an embodiment, the connection chamber set includes at least one connection chamber 31, the connection chamber 31 is disposed in a transverse direction, the connection holder 3 is provided with a first connection hole 32 for installing the locking member 4, and the first connection hole 32 is disposed in a longitudinal direction and penetrates through the connection chamber 31. Furthermore, be equipped with along the second connecting hole 12 of vertical setting on the first connecting piece 1, be equipped with along the second connecting hole 12 of vertical setting on the second connecting piece 2, retaining member 4 passes first connecting hole 32 and second connecting hole 12 and locks between first connecting piece 1, second connecting piece 2 and the connecting seat 3. Further, the number of the first connecting holes 32, the second connecting holes 12 and the second connecting holes 12 is the same, and the setting positions correspond, so that the locking member 4 simultaneously passes through the first connecting holes 32, the second connecting holes 12 and the third connecting holes 73 to lock the first connecting member 1, the second connecting member 2 and the connecting seat 3. Adopt this structural design to make retaining member 4 receive the shearing force under the effect of first connecting piece 1 and second connecting piece 2 to keep stable state, first connecting piece 1 and second connecting piece 2 exert perpendicular to 4 axial forces of retaining member to retaining member 4 towards opposite direction promptly, further prevent retaining member 4 not hard up, avoid first connecting piece 1, second connecting piece 2, the unblock of connecting seat 3 to break away from, make the structure more reliable and more stable. Furthermore, when the number of the connecting cavities 31 is one, the first connecting piece 1 and the second connecting piece 2 extend into the same connecting cavity 31, so that the first connecting piece 1 and the second connecting piece 2 can be connected at the same connecting position, the structure is simple, and the assembly and disassembly are quick and convenient.
Referring to fig. 3 and 11, in an embodiment, the connection cavity group includes two connection cavities 31 distributed along the longitudinal direction, the first connection member 1 extends into one of the two connection cavities 31, the second connection member 2 extends into the other connection cavity 31, and the two connection cavities 31 are arranged in a staggered manner along the longitudinal direction, so that the requirement on the installation space is reduced, and the universality is stronger. Optionally, one connection cavity includes at least one jack, and the jack transversely sets up, and when the jack quantity was a plurality of, a plurality of jacks distributed along longitudinal direction, the jack can also be the blind hole for the through-hole for first connecting piece and second connecting piece can stretch into the connection cavity can. Furthermore, the number and the positions of the jacks can be correspondingly arranged according to the number and the positions of the first support lug and the second support lug.
Referring to fig. 3 and 4, in an embodiment, one of the first connector 1 and the second connector 2 has a structural strength greater than the other. Alternatively, the structural strength of the first connecting member 1 and the second connecting member 2 may be made different by making a difference in thickness between the first connecting member 1 and the second connecting member 2, or the structural strength of the first connecting member 1 and the second connecting member 2 may be made different by providing a reinforcing structure in one of the first connecting member 1 and the second connecting member 2, or the structural strength of the first connecting member 1 and the second connecting member 2 may also be made different from the structural layout of the first connecting member 1 and the second connecting member 2. Furthermore, the first end of the second connecting piece 2 faces the first connecting piece, the first end of the second connecting piece 2 is provided with two second support lugs 21 which are longitudinally distributed, the second support lugs 21 are at least partially overlapped with the first support lugs 11, and the two second support lugs 21 are positioned between the two first support lugs 11, so that the structural strength of the first connecting piece 1 and the second connecting piece 2 is poor under the condition that a reinforcing structure is not separately additionally arranged or the thickness of the first connecting piece and the second connecting piece is changed, the parts are prevented from being damaged at the same time, and the loss is reduced.
Referring to fig. 3 and 4, in an embodiment, the locking member 4 may be a bolt, a ball-detent with a self-locking structure, or other structures capable of achieving connection locking. Furthermore, the ball head lock pin comprises a pin, one end of the pin is provided with a ball head protrusion, the other end of the pin is provided with a pressing structure for controlling whether the ball head protrusion protrudes out of the surface of the pin, and after the ball head lock pin is inserted into the connecting seat, the pressing structure is used for controlling the ball head protrusion to protrude out of the surface of the pin and be matched with a limiting structure in the connecting seat so as to limit the ball head lock pin to be separated from the connecting seat.
Referring to fig. 1, 2 and 3, in one embodiment, the present application further provides a drone, including a drone quick release mechanism as in any of the previous embodiments, further including an inner wing assembly 5 and an outer wing assembly 6, the inner wing assembly 5 being connected to the first connector 1, and the outer wing assembly 6 being connected to the second connector 2. The inner wing assembly 5 and the outer wing assembly 6 can be conveniently and rapidly disassembled, and the disassembling efficiency is improved.
Referring to fig. 1 to 4, 9 and 10, in an embodiment, the drone further includes a droop assembly 7, the inner wing assembly 5 and the outer wing assembly 6 are located on opposite sides of the droop assembly 7, and the inner wing assembly 5 and the outer wing assembly 6 are connected to the droop assembly 7 at the same connection location through the first connector 1 and the second connector 2, respectively. Optionally, the connecting seat 3 is installed in the hanging-up component 7, and each connecting cavity 31 of the connecting cavity group is arranged along the horizontal direction, openings 74 corresponding to and communicating with the connecting cavity group are arranged on two opposite sides of the hanging-up component 7, and the openings 74 are aligned with and communicate with the end portions of the connecting cavities, so that the first connecting piece 1 and the second connecting piece 2 can extend into the connecting cavities 31 from the openings 74. Further, the hanging-up components 7 are distributed along the head-tail direction of the unmanned aerial vehicle body. Furthermore, the connecting cavity can be a square cavity, so that the limiting is more reliable and stable. Further, the longitudinal direction is the Z direction, namely the vertical direction; the transverse direction is the X direction, namely the extending direction of the wings, and is vertical to the head and tail directions of the engine body; the body moves from head to tail in the Y direction. Further, the droop assembly 7 comprises a first droop skin 71 and a second droop skin 72, the first droop skin 71 and the second droop skin 72 are of U-shaped structures, the opening direction of the first droop skin 71 faces the opening direction of the second droop skin 72, and the first droop skin 71 and the second droop skin 72 are connected to form droop mounting cavities distributed along the head-to-tail direction of the airframe.
By adopting the structural design of the previous embodiment, the force of the vertical component 7 can be directly transmitted to the inner wing component 5 and the outer wing component 6 through the first connecting piece 1 and the second connecting piece 2, and the limiting of the inner wing component, the outer wing component and the vertical component in the Z direction and the course direction (Y direction) can be realized through the connecting seat. And install the connecting seat in the subassembly that hangs down, reduce and expose the structure in outside, reduce the protruding thing to reduce aerodynamic drag, be favorable to increasing the time of navigating, the structure is also neater and more pleasing to the eye. In addition, the interior of the vertical component adopts a hollow structure, so that the weight can be reduced, sufficient installation space can be provided for the connecting seats 3, the connecting seats 3 with different quantities can be conveniently installed according to requirements, the number of the connecting seats 3 is more flexible and convenient, and the universality is high.
Referring to fig. 1 to 4, 9 and 10, in an embodiment, a third connecting hole 73 is formed at the top of the hanging assembly 7 along the longitudinal direction, and the lower end of the locking member 4 extends into the hanging assembly 7 through the third connecting hole 73 to lock the first connecting member 1 and the second connecting member 2 with the connecting base 3. Install retaining member 4 at the top of the subassembly that hangs down, be convenient for observe the locking state and the direct operation retaining member of retaining member, increase the convenience, make the retaining member keep vertical decurrent motion trend under self action of gravity moreover, effectively prevent that the retaining member from breaking away from the subassembly that hangs down, favourable holding locking state improves structural reliability and security. Further, the number of the third connecting holes 73 may be set as required, and specifically, when there is one third connecting hole connected to the same connecting seat, two semicircular arcs of the third connecting hole may be respectively disposed on the first dropping skin 71 and the second dropping skin 72; when the third connecting holes connected with the same connecting seat are two, the two third connecting holes can be respectively arranged on the first vertical skin 71 and the second vertical skin 72, the structure is symmetrical, the stress is uniform, meanwhile, the first vertical skin 71 or the second vertical skin 72 can be further prevented from being separated from the connecting seat 3, and the structure is more stable and reliable.
Referring to fig. 1-4, in one embodiment, retaining member 4 can be connected to drop assembly 7 by a flexible connection. Further, retaining member 4 can be connected at the subassembly 7 that hangs down through flexible rope, and the retaining member is lost when preventing to take off the retaining member, avoids the equipment or dismantles the in-process part organism that drops.
Referring to fig. 1 to 8, in an embodiment, the structural strength of the first connector 1 is greater than the structural strength of the second connector 2. Adopt this structural design, when the overload value appears and is greater than the design value, outer wing assembly destroys in advance, and tail boom part and interior wing assembly can also keep intact, can save unmanned aerial vehicle after the subassembly that hangs down starts to and save a large amount of airborne equipment and load on the unmanned aerial vehicle, follow-up only need change the outer wing assembly of damage can, be favorable to falling the loss to minimumly.
Referring to fig. 1 to 6, in an embodiment, the inner wing assembly 5 includes an inner wing skin and an inner wing bridge mounted within the inner wing skin, the inner wing bridge being connected to the second end of the first connector 1. Optionally, the inner wing skin comprises a first inner wing skin 51 and a second inner wing skin 52, the first inner wing skin 51 is located above the second inner wing skin 52, and the first inner wing skin 51 and the second inner wing skin 52 are connected such that an inner wing installation cavity for installing the inner wing connection beam is formed between the first inner wing skin 51 and the second inner wing skin 52. Optionally, the quantity of first connecting piece 1 and interior wing tie-beam equals and corresponds the setting, and the quantity of first connecting piece and interior wing tie-beam can set up according to the intensity demand, and when the quantity of first connecting piece 1, interior wing tie-beam was greater than or equal to two, a plurality of first connecting pieces distributed along the head and the tail direction of organism, and a plurality of interior wing tie-beams distributed along the head and the tail direction of organism. Further, the inner wing connecting beam comprises a first inner wing connecting beam 53 and a second inner wing connecting beam 54 which are distributed along the head-to-tail direction of the engine body, one of the two first connecting pieces 1 is connected with the inner wing assembly 5 through the first inner wing connecting beam 53, and the other of the two first connecting pieces 1 is connected with the inner wing assembly 5 through the second inner wing connecting beam 54.
Referring to fig. 1 to 5, 7 and 8, in an embodiment, the outer wing assembly 6 comprises an outer wing skin and an outer wing connecting beam mounted within the outer wing skin, the outer wing connecting beam being connected to the second end of the second connector 2. Optionally, the outer wing skin includes a first outer wing skin 61 and a second outer wing skin 62, the first outer wing skin 61 is located above the second outer wing skin 62, and the first outer wing skin 61 and the second outer wing skin 62 are connected such that an outer wing installation cavity for installing the outer wing tie beam is formed between the first outer wing skin 61 and the second outer wing skin 62. Optionally, the quantity of second connecting piece 2 and outer wing tie-beam equals and corresponds the setting, and the quantity of second connecting piece and outer wing tie-beam can set up according to the intensity demand, and when the quantity of second connecting piece, outer wing tie-beam was greater than or equal to two, a plurality of second connecting pieces distributed along the head and the tail direction of organism, and a plurality of outer wing tie-beams distributed along the head and the tail direction of organism. Further, the outer wing tie-beam includes first outer wing tie-beam 63 and the outer wing tie-beam 64 of second that distributes along organism end to end direction, and one of them second connecting piece in two second connecting pieces 2 is connected with outer wing assembly 6 through first outer wing tie-beam 63, and another second connecting piece in two second connecting pieces 2 is connected with outer wing assembly 6 through second outer wing tie-beam 64.
The outer wing tie-beam is fixed with the outer wing skin again after being fixed with first connecting piece, and the inner wing tie-beam is fixed with the inner wing skin again after being fixed with the second connecting piece for the biography power route is shorter, hangs down the subassembly and directly passes power to inner wing tie-beam, outer wing tie-beam on, has guaranteed the intensity performance of structure when lightening structure weight.
Referring to fig. 1 to 10, in an embodiment, the first connector 1, the second connector 2, the connecting socket 3, the outer wing assembly 6, the inner wing assembly 5 and the suspension assembly 7 may be made of an aluminum alloy material or other lightweight materials. The weight is reduced, and meanwhile, the material cost and the processing cost are reduced.
The part quick-release mechanism of the unmanned aerial vehicle and the unmanned aerial vehicle have the advantages that the number of parts is reduced, the assembly and disassembly operations are simple, quick and convenient, the rapid folding or unfolding can be realized without tools, no part falls off in the disassembly and assembly process, the force transmission path of the structure is direct, the structure is simplified, the strength of the structure is ensured, the fault rate is low, the reliability is high, the cost is low, the weight is light, the mass production is convenient, the general interchangeability of each part is high, and the replacement is convenient after the part is damaged. This unmanned aerial vehicle flight operation in-process, the resistance is little, and the time of sailing is long, more can adapt to multiple operational environment.
In the description of the present specification, reference to the description of the terms "present embodiment," "example," "specific example," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing embodiments are merely illustrative of the principles and utilities of the present invention and are not intended to limit the invention. Any person skilled in the art can modify or change the above-mentioned embodiments without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which can be made by those skilled in the art without departing from the spirit and technical spirit of the present invention be covered by the claims of the present invention.
Claims (15)
1. An unmanned aerial vehicle part quick detach mechanism which characterized in that includes:
the first end of the first connecting piece is provided with two first support lugs distributed longitudinally and used for connecting a first component;
the first end of the second connecting piece is provided with two second support lugs distributed along the longitudinal direction and used for connecting a second component;
the connecting base is provided with a connecting cavity group for the first connecting piece and the second connecting piece to extend into; a first lug on the first end of the first connecting piece extends into the connecting cavity group, and a second lug on the first end of the second connecting piece extends into the connecting cavity group and is at least partially overlapped with the first lug on the first end of the first connecting piece; the shape of the connecting cavity group is matched with the shapes of the first connecting piece and the second connecting piece, and the connecting cavity group is used for limiting the unidirectional movement of the first connecting piece and the second connecting piece in the horizontal direction, the rotation of the first connecting piece and the second connecting piece in the horizontal direction, the movement of the first connecting piece and the second connecting piece in the vertical direction and the rotation of the first connecting piece and the second connecting piece in the vertical direction;
the locking piece penetrates through the overlapped part of the first connecting piece and the second connecting piece and locks the first connecting piece, the second connecting piece and the connecting seat;
the connecting cavity group comprises at least one connecting cavity, the connecting cavity is arranged along the transverse direction, a first connecting hole for installing a locking piece is formed in the connecting seat, and the first connecting hole is arranged along the longitudinal direction and penetrates through the connecting cavity; the first connecting piece with be equipped with along the second connecting hole of vertical setting on the second connecting piece, the retaining member passes first connecting hole with the second connecting hole will first connecting piece, the second connecting piece with lock between the connecting seat.
2. The quick release mechanism for unmanned aerial vehicle components of claim 1, wherein: the first connecting piece and the second connecting piece are positioned on two opposite sides of the connecting seat.
3. The quick release mechanism for unmanned aerial vehicle components of claim 1, wherein: the first end of the first connecting piece faces the second connecting piece.
4. The quick release mechanism for parts of an unmanned aerial vehicle of claim 3, wherein: the first end of the second connecting piece faces the first connecting piece; the two second lugs are located between the two first lugs, or the two first lugs are located between the two second lugs, or the two first lugs and the two second lugs are alternately distributed along the longitudinal direction.
5. The quick release mechanism for components of an unmanned aerial vehicle of claim 1, wherein: connect the cavity group including two along the connection chamber of longitudinal distribution, first connecting piece stretches into two connect one of them in the chamber, the second connecting piece stretches into two connect another in the chamber.
6. The quick release mechanism for components of an unmanned aerial vehicle of claim 1, wherein: one of the first connecting piece and the second connecting piece has a structural strength greater than that of the other.
7. The quick release mechanism for components of an unmanned aerial vehicle of claim 1, wherein: the locking piece is a bolt or a ball head locking pin with a self-locking structure.
8. An unmanned aerial vehicle, its characterized in that: the rapid part dismounting mechanism of the unmanned aerial vehicle comprises the rapid part dismounting mechanism of any one of claims 1 to 7, and further comprises a vertical component, an inner wing component and an outer wing component, wherein the inner wing component is connected with a first connecting piece, the outer wing component is connected with a second connecting piece, the inner wing component and the outer wing component are positioned on two opposite sides of the vertical component and are respectively connected with the vertical component through the first connecting piece and the second connecting piece, the connecting seat is installed in the vertical component, the connecting cavity group is arranged along the transverse direction, and openings corresponding to and communicated with the connecting cavity group are arranged on two opposite sides of the vertical component; the top of the vertical component is provided with a third connecting hole which is arranged along the longitudinal direction, and the lower end of the locking component penetrates through the third connecting hole and extends into the vertical component to connect the first connecting piece and the second connecting piece with the connecting seat for locking.
9. The drone of claim 8, wherein: the retaining member is connected with the hanging assembly through a flexible connecting structure.
10. The drone of claim 8, wherein: the first connector has a structural strength greater than a structural strength of the second connector.
11. The drone of claim 8, wherein: the inner wing assembly includes an inner wing skin and an inner wing tie beam mounted within the inner wing skin and coupled to the second end of the first connector.
12. The drone of claim 8, wherein: the outer wing assembly includes an outer wing skin and an outer wing tie beam mounted within the outer wing skin and coupled to the second end of the second link.
13. A drone according to claim 12, characterised in that: the first connecting piece, the second connecting piece, the connecting seat, the outer wing assembly, the inner wing assembly and the hanging assembly are made of aluminum alloy materials.
14. The drone of claim 8, wherein: the drooping assembly comprises a first drooping skin and a second drooping skin, the first drooping skin and the second drooping skin are of U-shaped structures, the opening direction of the first drooping skin faces the opening direction of the second drooping skin, the first drooping skin and the second drooping skin are connected to form a drooping installation cavity distributed along the head and tail directions of the body, and the connecting seat is installed in the drooping installation cavity of the drooping assembly.
15. A drone according to claim 14, characterized in that: when one third connecting hole is formed in the connecting base, two semicircular arcs of the third connecting hole can be respectively arranged on the first vertical skin and the second vertical skin; when there are two third connecting holes connected to the same connecting seat, the two third connecting holes may be respectively disposed in the first and second drooping skins.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105522497A (en) * | 2015-11-27 | 2016-04-27 | 沈阳飞机工业（集团）有限公司 | Method for positioning parts such as aircraft skins and wall plates of multiple models |
| CN107031819A (en) * | 2015-11-18 | 2017-08-11 | 空中客车德国运营有限责任公司 | Folding wing for aircraft and the aircraft with folding wing |
| CN212605769U (en) * | 2020-05-27 | 2021-02-26 | 青岛中科方舟航空科技有限公司 | Connection structure and compound wing unmanned aerial vehicle of tail stay pole and wing |
| CN113955082A (en) * | 2021-12-02 | 2022-01-21 | 北京航空航天大学 | Light control surface and hinge structure suitable for solar unmanned aerial vehicle |
Family Cites Families (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3737651A1 (en) * | 1987-11-06 | 1989-05-18 | Gerd Baer | DEVICE FOR A FOLDING LIFTBOARD |
| DE69735994T2 (en) * | 1996-03-22 | 2007-01-11 | The Boeing Co., Seattle | Method for mounting wing beams and ribs with tight tolerances |
| CN103963958B (en) * | 2014-04-21 | 2015-12-09 | 西工大常熟研究院有限公司 | Unmanned plane wingfold mechanism |
| GB2528231A (en) * | 2014-04-24 | 2016-01-20 | Airbus Operations Ltd | An aircraft with a foldable wing tip device |
| CN104260876B (en) * | 2014-09-30 | 2016-07-06 | 浙江水利水电学院 | The outer wing folding and unfolding mechanism of a kind of morphing aircraft |
| US10106240B2 (en) * | 2015-07-13 | 2018-10-23 | The Boeing Company | Pinned fuselage-to-wing connection |
| CN107651162A (en) * | 2017-09-27 | 2018-02-02 | 西安冰果智能航空科技有限公司 | A kind of unmanned plane wing quick assembling mechanism |
| CN108657414B (en) * | 2018-05-15 | 2020-12-11 | 北京航空航天大学 | Device and method for connecting central wing, outer wing and tail boom of unmanned aerial vehicle |
| CN108750072A (en) * | 2018-06-06 | 2018-11-06 | 东汉太阳能无人机技术有限公司 | A kind of wing and unmanned plane of unmanned plane |
| CN109808868A (en) * | 2018-11-22 | 2019-05-28 | 成都飞机工业（集团）有限责任公司 | A kind of interior outer wing docking structure of small drone |
| GB2580345A (en) * | 2019-01-02 | 2020-07-22 | Airbus Operations Ltd | Actuator assembly for moving an aircraft wing tip device |
| US11655019B2 (en) * | 2020-05-27 | 2023-05-23 | The Boeing Company | Method and system for coupling a vertical stabilizer to an aircraft fuselage |
| CN214930551U (en) * | 2021-05-19 | 2021-11-30 | 西安探索鹰航空科技有限公司 | Oil moves unmanned aerial vehicle modular structure |
| CN215155584U (en) * | 2021-06-02 | 2021-12-14 | 沃飞长空科技(成都)有限公司 | Quick assembly disassembly structure of unmanned aerial vehicle section |
-
2022
- 2022-03-28 CN CN202210308853.6A patent/CN114476015B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107031819A (en) * | 2015-11-18 | 2017-08-11 | 空中客车德国运营有限责任公司 | Folding wing for aircraft and the aircraft with folding wing |
| CN105522497A (en) * | 2015-11-27 | 2016-04-27 | 沈阳飞机工业（集团）有限公司 | Method for positioning parts such as aircraft skins and wall plates of multiple models |
| CN212605769U (en) * | 2020-05-27 | 2021-02-26 | 青岛中科方舟航空科技有限公司 | Connection structure and compound wing unmanned aerial vehicle of tail stay pole and wing |
| CN113955082A (en) * | 2021-12-02 | 2022-01-21 | 北京航空航天大学 | Light control surface and hinge structure suitable for solar unmanned aerial vehicle |
Non-Patent Citations (1)
| Title |
|---|
| 某轻型飞机虚拟装配关键技术研究;吕思超;《中国优秀博硕士学位论文全文数据库(硕士)工程科技Ⅱ辑》;20170315;全文 * |
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